JPS62122900A - Extension mast - Google Patents

Abstract

(57) [Summary] This bulletin contains application data before electronic filing, so abstract data is not recorded.

Description

DETAILED DESCRIPTION OF THE INVENTION [Field of Industrial Application] The present invention relates to an extendable mast used as the basic structure of a space facility that stays in orbit for a long period of time, and particularly relates to an extendable mast used as the basic structure of a space facility that stays in orbit for a long period of time. Regarding mast extension and storage structure.

[Technology background]

It stays in space for a long time, such as in Earth orbit, and performs various experiments.
Recently, many countries are planning the construction of large-scale space facilities to provide services.

Such space facilities must be constructed using basic structures launched from the ground. At present, the basic structure is an extendable mast that can be stored compactly on the ground and expanded widely in space. In the future, this extension mast is expected to be used for multiple purposes, not only as a support structure for mission aircraft used for experiments, but also as the basic structure of large-scale structures such as large antennas and platforms.

[Conventional technology]

Such extension j1 (as a mast, conventionally, for example, the 24th
There are things like those shown in Figures 26 to 26.
o, 045 (IB)R, see page 16], Figure 24 shows:
This shows the stored state of the mast structure 1 that is extended in a specific direction on the orbit. The mast structure 1 is stored in this state on the ground, and the restraint is released on the target trajectory. The mast member release method is a pyrotechnic method using a gunpowder breaking means, a pyrotechnic method using a solenoid, etc.
When the restraint, which is performed by a simple external auxiliary mechanism such as a mechanical one using a spring or the like, is released, the axial member 3 constituting the mast structure l will self-recover by the restoring energy due to the The frame member 2 expands and stretches out, forming a plane perpendicular to the direction of extension. FIG. 26 shows the mast structure 1 in a completely extended state. The triangular frame members 2 are arranged perpendicularly to the same imaginary axis 8, and the opposing sides of the opposing frame members 2 are connected by three axial members 3, 4.5. 6 is a truss member formed of a flexible member that becomes a diagonal member when the mast structure 1 is deployed.

A similar technology was disclosed in the ``Space, Aircraft, and Ocean'' column of the Nikkei Sangyo Shimbun dated April 1, 1985. Also,
This extendable mast has a storage compartment for storing and transporting the mast structure to the destination orbit.

[Problem that the invention seeks to solve]

By the way, in such a conventional extendable mast, when the restraint of the mast member is released, the mast expands all at once until the final stage, and cannot be retracted thereafter. However, in order to utilize the extension mast for multiple purposes in the future, it is necessary not only to continuously extend the mast structure by 1+4, but also to store it after extension, re-extend it after storage, and stop it at any time during extension and storage. Various functions are required. What is the function of storing after stretching?

This is because when a mission aircraft is installed at the tip of the mast, extravehicular activities required for maintenance or replacement of the mission aircraft can be performed quickly and easily.
This is because the function of arbitrary stopping during storage is important in expanding the degree of freedom of geometrical shapes in the construction of large-scale space structures.

Additionally, if it becomes possible to store it in orbit, it will also be possible to retrieve it to the ground if necessary.

Therefore, an object of the present invention is to enable continuous extension of the mast structure, retraction and storage after extension, and arbitrary stopping during extension and storage.

[Means for solving problems]

In order to achieve the above-mentioned objects and solve the problems, an extension mast of the present invention has a mast structure in which a plurality of frame members, which are to be disposed perpendicularly on the same imaginary axis, are connected by an axial member. Store the body and the mast structure and move to the target position 11! In an extendable mast consisting of a storage compartment for transport, a hinge mechanism is provided at an intermediate position of the axial member, and the mast structure is provided in the storage compartment while capturing a connecting portion between the axial member and the frame member. A mast driving means capable of reciprocating in conjunction with the direction of extension of the body is provided, and a mast storage means is provided which bends the axial member by acting on the hinge mechanism when the mast driving means retracts the mast structure.

[Effect]

Since the present invention provides a hinge mechanism at the intermediate portion of each axial member constituting the mast structure, the mast structure can be stored on the ground by bending each axial member. Further, the present invention is provided with a mast driving means that can capture the connecting portion connecting the axial member and the frame member and move it in the extension direction of the mast, so that the mast structure can be pulled out from the storage compartment on the desired trajectory. It can be extended and the mast structure can be retracted on the track. Furthermore, since a mast storage means is provided which acts on the hinge mechanism of the axial members and bends each axial member when the mast is retracted, the mast structure can be stored on the track. Furthermore, by stopping the operation of the mast driving means in response to a command from the spacecraft, extension and retraction of the mast structure can be stopped at will.

〔Example〕

Hereinafter, the present invention will be described in detail based on the accompanying drawings.

FIG. 1 shows the basic configuration of an example of an extendable mast according to the present invention.

This extension mast lO has a mast structure 11 to be extended on a target trajectory, and a canister 12 as a storage compartment for storing this mast structure 11. Solenoid 14 as a mast driving means for extending and retracting the
．． 15 and a solenoid 16 as a mast storage means.

Each component is explained as follows.

As shown in FIG. 2, the mast structure 11 is a unit consisting of a frame member 18 arranged vertically in parallel to the same virtual axis 17, and an axial member 19 connecting opposite sides of the frame member 18. Multiple masts M in 17 directions of virtual axis (M1 to Mn)
Connect and form. 20 is a frame member 18 and an axial member 1
This is a connecting member for connecting 9. In addition, a hinge mechanism 21 as described later is provided in the intermediate portion of each axial member 19, and each axial member 19 is made bendable as shown in FIG. It can be folded. Therefore, this mast structure 11 can be extended in the direction of the imaginary axis 17 from the canister 12 as a storage compartment as shown in FIG. 4, and can be stored in the canister 12 as shown in FIG. becomes. When stored, the stack holders 22 provided in the canister 12 hold and fix the four corners of each frame member 18, as shown in FIG.

7 and 8 show a specific configuration example of the canister 12 in FIG. It is thermal insulation. This thermal insulation 25 is divided into four parts, for example.
As shown in FIG. 9, the winter jacket is secured using a fastener 26. In addition, 27 is a longitudinal trunnion that serves as a load support point during launch, 28 is a support fixture that serves as an input load support point during launch to longitudinal trunnion 27, and 29 is fixed to a keel fitting such as a space shuttle. , a keel trunnion that serves as a load support point on the launch surface, and 30 is a handle for nodling operations by the space shuttle and the space station's remote manipulators in orbit. Further, 32 is a canister fixture for fixing the canister 12 to the space base with fasteners, and 33 is a mast fixture for connecting the base end frame of the mast structure 11 to the base of the side frame of the canister 12 with fasteners. be. In addition, the mast structure 11
A strand 35 is provided to maintain structural stability during extension. S is a strand storage portion that extends and stores the strand 35 as the mast structure 11 is extended and stored.

The canister 12 having such a configuration includes solenoids 14 and 15 as mast driving means that can move in the axial direction within the dust cover 36 disposed at four corners of the canister 12, and a solenoid 1 as a mast storage means.
6 will be provided. The dust cover 36 protects the mast driving means from radiant heat in orbit and space dust, and also protects the mast driving means from vibrations during launch. Specifically, the solenoids 14 and 15 are connected to a support frame 38 that operates integrally with a ball screw 37, as shown in FIG.
placed above. The ball screw 37 is moved along the mast extension direction by rotating the tube nut 43 by the rotational torque from the drive motor 42 that is transmitted from the driving gear 40 to the driven gear 41 via the reduction mechanism,
The support frame 38 is driven along the guide 45. The operation of the drive motor 42 is controlled by a control signal from the spacecraft. The driving gear 40 is actually located behind the driven gear 41 in the figure, but for ease of understanding, the reference numeral 47 in Figure 0 is shown above the driven gear 41. The wall on the spacecraft side, 44 is a case body that encloses the tube nut 43, and 46 is the drive motor 4.
This is the drive shaft that should be linked to 2. Incidentally, as shown in FIG. 11, by rotating the ball screw 37 and moving the tube nut 43, the support frame 38 integrated with the tube nut 43 may be made movable. Honor Mast M
Move by minutes. When the mast structure is extended and stored, the levers, axial member 19 and frame member 18 as shown in FIG.
The pins 14a, 15a of either one of the solenoids 14, 15 enter the post 39 provided on the connecting member 20 that connects the two, latching the connecting portion and operating the mast structure 11 to extend and retract. Returning to FIGS. 7 and 8, 48 is a wire neck for supplying power to the tip of the mast structure 11, and 49 is for supplying fluid, gas, etc. to the tip of the mast structure 11. These flexible hoses are pulled out and wound up as the mast structure 11 is extended and stored by driving drums 73 and 74 by drive motors 71 and 72, respectively. 75 is a pulley. Further, 76 is a lock plate disposed at the rear end of the canister 12, and 77 is disposed on the lock plate 76, and when it is detected that any one of the support frames 38 has reached a predetermined position, the drive motor This is a limit switch that stops the 42, 71, and 72.

Next, the operation will be explained. For simplicity, mast structure 11
We will explain the extension and storage of the strike M at a specific middle position. During extension, the pin 14a of the extension solenoid 14 disposed on the support frame 38 as shown in FIG.
latches the boss of the connecting member 20f provided on the extension direction side frame member 18f and moves in the extension direction of the mast (direction of arrow A in the figure). At this time, since the movement of the unlatched frame member 18r on the canister side is restricted by the stack holder 22 in the canister 12, the axial member 18r
The hinge mechanism 21 of 9 expands as the solenoid 14 moves. When movement of the support frame 38 by a predetermined distance is detected by the limit switch 77, the solenoid 14 releases the latch of the connecting member 20f, and the canister 12 is opened again.
Return to the side, latch the next connecting member 20r, and move it in the extension direction. The support frame 38 and the solenoid 14 repeat this operation to sequentially extend the unit mast M.

On the other hand, when storing the unit mass) M, as shown in FIG.
0r is latched and the frame member 18r is stored in the canister 12. When the frame member 18r moves to a predetermined position (in the direction of arrow B in the figure), the support frame 38 is moved as shown in FIG.
The upper solenoid 16 presses the middle portion of the axial member 19 to make the axial member 19 bendable. Next, the storage solenoid 15 launches the connecting member 20f of the extension side frame member 18f and moves it into the canister 12. At this time, the axial member 19 is bent inward by the hinge mechanism 21, and the unit mast M is completely attached to the canister 12.
It will be stored inside.

17 to 20UA show specific configuration examples of the hinge mechanism 21 of the axial member 19. In the figure, 50 is a hinge provided at the intermediate portion of the axial member 19, and 51 is a link mechanism. The link 6't4W5t has one end rotatably fixed to the axial member 19 by a pin joint 52.53, and the other end of a link arm 54.55 is connected by a pin joint 56. Further, a torsion spring 57 is provided at the binge joint 52 located on the extension direction side of the axial member 19 to press the link arm restraining wall 58. This torsion spring 57 causes the link mechanism 51 to generate a launch force at the over-center position.

60 is a partition wall. A cylindrical hole 61 is formed in the partition wall 60 on the spacecraft side, and a spring 62 is inserted into the hole 61.
and an operating rod 63 for canceling the launch of the link mechanism 51. At both ends of the operating rod 63 are disk-shaped suppressing portions 64.
Form 65. 66 is a stopper that limits the movement of the operating rod 63. Further, 68 is a latch release pin that can be rotated around a pin fulcrum 69, and has a tip portion 68a on the spacecraft side.
is arranged between the pressing portion 64 and the spring 62. Further, the extension side tip portion 68b is arranged at a position where the joint portion of the link arm 54, 55 can be suppressed.

According to the hinge mechanism 21, when the axial member 19 is extended, the spring 62 causes the pressing portion 64 to press against the stopper 66.
Since the latch release pin 68 is pressed to this position, the latch release pin 68 will not malfunction to release the link mechanism 51 due to vibrations, shocks, or the like. When bending the axial member 19, the solenoid 16 presses the suppressing portion 65 of the operating rod 63. Then, the other suppressor 6
4 presses the spacecraft side tip 68a of the latch release pin 68, and the pin joint 56 is pressed by the extension side tip 68b.
Press down. As a result, the launch force of the link mechanism 51 in the over-center position is released, and the axial member 1
9 is in a bendable state. However, in this state, the link mechanism 51 returns to the over-center position due to the force of the torsion spring 57, so the solenoid pin 15a serving as the mast driving means pulls the frame member 18f toward the canister 12, and the link mechanism 51 returns to the over-center position. Axial member 1 up to a bending angle that does not start rotating until
Bend 9.

This operation causes the axial member 19 to move toward the canister 1.
2, it is bent as shown in Figures m18 and 19. The hinge mechanism 21 has a hole 70 formed in the axial member 19, as shown in FIG.
．． It can also be constructed by arranging 55 coupling parts. In this case, if the connecting part of the link arms 54 and 55 is pressed from the hole 70 by the solenoid 16 as a mast storage means, +i
? The axial member 19 can be bent similarly to the hinge mechanism described in j.

Note that the movement method of the support frame 38 on which the solenoids 14, 15, and 16 are disposed is the same as that of the canister 1 as in the previous embodiment.
Not limited to reciprocating interlocking that goes only in the extension direction from within the second
As shown in Figure 1, it can also be moved from the canister 12 to the spacecraft side in one canter. Further, as shown in FIG. 22, support frames 38 provided above and below the canister 12
may be moved alternately. Furthermore, as shown in FIG. 21, the support frame 38 may be bent via a link 59, and a solenoid or the like may be provided at the tip thereof to move the solenoid along the axial member.

〔Effect of the invention〕

As explained above, the present invention provides continuous extension of a mast structure to be extended on a track, I! ! Since it is possible to store, extend, and store the spacecraft, it is possible to easily carry out extravehicular activities necessary for maintenance and replacement of mission aircraft, and it is also possible to improve the shape of geometric shapes in the construction of large-scale space structures. You can expand your freedom. Also, by storing it in orbit, it becomes possible to retrieve it to the ground.

[Brief explanation of drawings]

Fig. 1 is a basic configuration diagram of an example of an extendable mast according to the present invention;
3 and 3 are basic configuration diagrams of an example of the mast structure according to the present invention, FIG. 4 is a diagram showing the expanded state y exit side of the mast structure according to the present invention, and FIGS. 5 and 6 are diagrams illustrating the mast structure according to the present invention. FIG. 7 is a diagram showing an example of a storage compartment (canister) according to the present invention, and FIG.
The figure is a view taken along arrow A in FIG. 7, FIG. 9 is a sectional view taken along the line IX-IX in FIG. 7, and FIGS. Figure 12 is the 10th
13 to 16 are explanatory diagrams of the operation of the extension mast according to the present invention, FIG. 17 is a sectional view showing an example of the hinge mechanism of the axial member according to the present invention, and FIG. The figure is a sectional view showing the bent shape yE of the axial member, and FIG.
8 is a view in the direction of arrow B in FIG. 8, FIG. 20 is a sectional view showing another example of the hinge mechanism according to the present invention, and FIGS. 21 to 23 are views showing other embodiments of the extendable mast according to the present invention. 24 to 26 are diagrams showing conventional extendable masts. 11... Mast structure 12... Canister (storage compartment) 14
．． 15... Solenoid (mast driving means) 16...
Solenoid (mast storage means) 18.18f, 18r・
...Frame member 19...Axial member 20.2Of, 20r...-i! l! Ayu parts 21...
・Hinge mechanism 37...Ball screw 38...Support frame 42...Drive motor No. 1E 10 (arbitration mast for lunchtime) No. 211A Fig. 3 21 (Constitution) Fig. 8 Fig. 11 Fig. 18 Blp. Figure 19 1゜5'455 Figure 20

Claims (1)

[Claims] A mast structure formed by connecting a plurality of frame members arranged orthogonally on the same imaginary axis by an axial member, and a storage compartment for storing and transporting the mast structure to a target position. In the extensible mast, a hinge mechanism is provided at an intermediate position of the axial member, while the storage compartment captures a connecting portion between the axial member and the frame member, and has a hinge mechanism with respect to the extension direction of the mast structure. An extendable mast, characterized in that it is provided with a mast driving means capable of reciprocally interlocking movement, and also provided with a mast storage means that acts on the hinge mechanism to bend the axial member when the mast driving means retracts the mast structure.